Robust nonlinear attitude control of spacecraft with flexible structures

Yiing Yuh Lin, Gern Liang Lin

研究成果: Paper同行評審

3 引文 斯高帕斯(Scopus)


An approach incorporating the input-output feedback linearization and the sliding mode control is presented in this paper for the simultaneous multiaxis reorientation of a rigid spacecraft with flexible structures. Modeling of the dynamic system gives a set of coupled ordinary and partial differential equations, which describe the attitude dynamics of the spacecraft and the motions of the flexible structures, respectively. To apply the proposed attitude control law, the set of nonlinear equations governing the attitude motions were transformed into modified Rodrigues parameters(MRP) representation. Deformations of the flexible structures are assumed small under the control efforts and the governing equations are simplified by applying the mode-shape functions. The attitude feedback gain considering structure stabilization and system uncertainties is further determined by the use of Lyapunov function which ensures the control system to be stable and robust. Major advantage of the method is that only three attitude torque actuators in the hub are required for the proposed control law. Attitude detumbling to reorientation of a model spacecraft was tested and the simulation results were included.

出版狀態Published - 2000 十二月 1
事件Astrodynamics Specialist Conference 2000 - Dever, CO, United States
持續時間: 2000 八月 142000 八月 17


OtherAstrodynamics Specialist Conference 2000
國家/地區United States
城市Dever, CO

All Science Journal Classification (ASJC) codes

  • 航空工程
  • 天文和天體物理學


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